Air engine high altitude test-bed intake and exhaust system

Abstract

The application provides an aero-engine high-altitude test bed intake and exhaust system, and belongs to the technical field of intake and exhaust systems, and comprises the following steps: obtaining a flowchart of preset test conditions and an intake and exhaust system, and selecting a suitable test cabin as a first test cabin based on the preset test conditions; performing data analysis based on the preset test conditions to obtain a target working condition, and calculating the operation of each valve based on the target working condition; monitoring the actual operation working condition of the test cabin in real time, and obtaining feedback information based on the real-time detection result; inputting the feedback information into a feedback-regulation scheme mapping table, determining different regulation schemes corresponding to different feedback information, and adjusting the operation working condition based on the regulation scheme. The test cabin provides different temperature and flow rate intake conditions for the engine or engine components in the test cabin, so that different test working conditions are simulated, and the simulation demand is further met.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to an intake and exhaust system for an aero-engine high-altitude test stand. Background Technology

[0002] High-altitude test stands for aero-engines are essential key research facilities for high-altitude, high-speed aircraft power plant development centers. Aero-engine engineering is large-scale, involves significant investment, is highly challenging, and technically complex. Among these, the intake and exhaust systems of the high-altitude test stands play a crucial role as a major component. To meet the intake requirements of aero-engines under complex high-altitude conditions, an intake and exhaust system capable of simulating different altitudes and Mach numbers is needed. However, existing publicly available information does not provide a complete high-altitude test stand intake and exhaust system; only partial components are available, which cannot meet the current testing needs of high-altitude test stands.

[0003] Therefore, the present invention provides an intake and exhaust system for a high-altitude test stand for an aero-engine. Summary of the Invention

[0004] This invention provides an intake and exhaust system for a high-altitude test bench for aero-engines, used for high-altitude testing of the entire engine or its components. The high-altitude simulation test bench mainly simulates the flight state and altitude of aero-engines at different altitudes within a high-altitude test chamber, thereby evaluating or assessing the engine's high-altitude performance, functional characteristics, and starting characteristics, etc. As an important component of the high-altitude test bench, this system provides intake conditions with different temperatures and flow rates for the engine or engine components within the test chamber, thereby simulating different test conditions.

[0005] This invention provides an intake and exhaust system for a high-altitude test stand of an aero-engine, comprising:

[0006] Information acquisition module: Acquires preset test conditions and structural diagrams of the intake and exhaust systems;

[0007] Information analysis module: performs data analysis on the preset test conditions to obtain the target operating conditions, and determines the operating status of each valve in the exhaust pipe specified in the different test chambers in the structural diagram based on the target operating conditions;

[0008] Real-time monitoring module: The simulation test chamber is tested and monitored according to the determined operating conditions, and the simulation feedback information is obtained.

[0009] Information mapping module: Inputs the simulated feedback information into the feedback-adjustment scheme mapping table to determine the information to be adjusted that exists in the corresponding simulated feedback information;

[0010] Adjustment module: Based on the adjustment information of different test chambers, the module adjusts the components of the intake and exhaust system and / or adjusts the valve operation under the corresponding test conditions.

[0011] Preferably, the intake and exhaust system includes test chamber 1 and test chamber 2;

[0012] Specifically, when the preset test conditions are related to temperature, the test chamber to be simulated is determined to be test chamber 1; when the preset test conditions are related to pressure, the test chamber to be simulated is determined to be test chamber 2.

[0013] Preferably, the intake and exhaust system further includes:

[0014] Low-temperature air intake pipe, normal-temperature air intake pipe, high-temperature air intake pipe, gas transmission pipe, exhaust tower 1, exhaust tower 2, mixer, rectifier section 1, rectifier section 2, test chamber 1, test chamber 2, spray section 1, spray section 2, spray tower and oil removal equipment, air extractor and valves;

[0015] The valves include: valve D1, valve D2, valve D3, valve D4, valve D5, valve D6, valve D7, valve D8, valve D9, valve D10, valve D11, valve D12, valve D13, valve D14, valve D15, valve D16, valve D17, and valve D18.

[0016] Preferably, the connection relationships between the components include:

[0017] Valve D1 is the ambient temperature inlet valve. Valve D3 is connected to exhaust tower 1 after valve D1. Valve D2 is the cryogenic inlet valve. Valve D4 is connected to exhaust tower 1 after valve D2. Ambient temperature gas enters the gas delivery pipeline through valve D1, is diverted by valve D3, and then reaches mixer 1 through valve D5. Cryogenic gas enters the gas delivery pipeline through valve D2, is diverted by valve D4, and then reaches mixer 1 through valve D6. Mixer 1 is connected to rectifier section 1, which is located after mixer 1. Valves D7 and D8 are connected to rectifier section 1, and are located after rectifier section 1. Valves D7 and D8 are connected to test chamber 1. The gas output from rectifier section 1 reaches test chamber through valve D7 or valve D8 according to its flow rate. 1. Spray section 1 is connected to test chamber 1 after it. D9 valve is connected to spray section 1 after it. Spray tower and oil removal equipment and D10 valve are connected to D9 valve after D9 valve. D11 valve is connected to spray tower and oil removal equipment after it. Evacuation fan is connected to D11 valve after D11 valve. Exhaust tower 2 is connected to D10 valve after D10 valve. If the test conducted in test chamber 1 is a ground test, the gas output from spray tower 1 passes through D9 valve and then through D10 valve to reach exhaust tower 2. If the test conducted in test chamber 1 is a high-altitude test, the gas output from spray section 1 passes through D9 valve to spray tower and oil removal equipment and then through D11 valve to reach extraction fan.

[0018] Valve D12 is located between valves D2 and D6 and is connected to rectifier section 2. Cryogenic gas, after being diverted by valve D4, can reach rectifier section 2 via valve D12. Valve D13 is located between valves D1 and D5 and is connected to rectifier section 2. Room temperature gas, after being diverted by valve D3, reaches rectifier section 2 via valve D13. Valve D14 is the high-temperature inlet valve, connected to rectifier section 2. High-temperature gas reaches rectifier section 2 after passing through valve D14. Valve D15 is located after rectifier section 2 and connected to it. Valve D16 and D17 are located between valve D15 and valve D17. The gas is connected to valve D15, and then to test chamber 2, which is connected to valves D16 and D17. Test chamber 2 is located after valves D16 and D17. The gas output from rectifier section 2 passes through valve D15 and then, depending on the flow rate, passes through valve D16 or D17 to reach test chamber 2. Spray section 2 is located after test chamber 2 and connected to it. Valve D18 is located after spray section 2 and connected to it. Exhaust tower 2 is located after valve D18 and connected to it. The gas output from test chamber 2 first passes through spray section 2, and then passes through valve D18 to reach exhaust tower 2.

[0019] Preferably, the information analysis module includes:

[0020] The process analysis unit is used to analyze the preset test conditions to obtain the test process, and to determine the specific operating status of each valve in the structure diagram based on the test process;

[0021] The test procedure is the target operating condition.

[0022] Preferably, the process analysis unit includes:

[0023] The test procedure parsing block is used to parse the test procedure and determine the test attributes of the test procedure;

[0024] When the test attributes are related to test chamber 1, close valves D12 and D13 to disconnect the compressed air from test chamber 2. Based on the flow rate at the operating point in the preset test conditions, select to open valves D7 or D8, and open valves D1 and D2 to allow low-temperature air and room-temperature dry air to pass through. Based on the flow rate and temperature at the target operating point in the preset test conditions, roughly adjust the opening of valves D3 and D4. Then adjust valves D5 and D6. Through the parameter feedback from the temperature and pressure sensors and flow meters on the pipeline, precisely adjust to the required air intake operating point of test chamber 1. The compressed air is mixed in mixer 1 to obtain compressed air with a uniform temperature. It flows through the rectifier section 1 to obtain compressed air with a uniform flow field, and then enters test chamber 1.

[0025] If the temperature of the compressed air rises after passing through test chamber 1, it will be cooled down by water spraying in spray section 1, thus reducing the exhaust temperature.

[0026] If test chamber 1 is conducting a ground test, then open valve D10 and the exhaust gas will directly enter the exhaust tower;

[0027] Otherwise, close valve D10 and open valve D11. The exhaust gas passes through the spray tower and oil removal equipment for secondary cooling, and unburned fuel in the exhaust gas is removed. Finally, the exhaust gas meets the requirements for entering the extraction unit and enters the extraction unit.

[0028] Preferably, the test procedure parsing block is further used for:

[0029] When the test attribute is related to test chamber 2, based on the temperature requirements of the air intake condition in the preset test conditions, select to open or close valves D12, D13, and D14.

[0030] If a high-temperature test is to be conducted, close valves D12 and D13, open valve D14, and select to open valve D16 or D17 based on the flow rate under the preset test conditions. The high-temperature compressed air flows through the rectifier section 2 into the test chamber 2, and the exhaust is discharged into the exhaust tower 2 after being cooled by the spray section 2.

[0031] Otherwise, close valve D14 and open valves D1 and D2 to allow low-temperature gas and room-temperature dry gas to pass through. Based on the flow rate and temperature of the target operating point in the preset test conditions, the flow rate and temperature are roughly adjusted by adjusting the opening of valves D3 and D4. Then, valves D12 and D13 are adjusted, and the required air intake operating point of test chamber 2 is precisely adjusted by the parameter feedback from the temperature and pressure sensors and flow meters on the pipeline. After flowing through the rectifier section 2, the mixed gas enters test chamber 2. The exhaust gas from test chamber 2 is cooled by the spray section and then discharged into the exhaust tower.

[0032] Preferably, the real-time monitoring module includes:

[0033] The data calculation unit is used to obtain standard operating status data of the test chamber to be simulated under the corresponding working conditions in the preset test environment based on the test process.

[0034] The data monitoring unit is used to collect the actual operating status of the corresponding operating point during the test based on the sensor set at the corresponding operating point in the test chamber to be simulated, wherein the actual operating status is related to the detection data of the sensor type of the sensor set at the corresponding operating point;

[0035] The feedback acquisition unit is used to compare the standard operating data of the same sensor with the real-time operating status data to obtain simulated feedback information.

[0036] Preferably, the information mapping module includes:

[0037] The mapping acquisition unit is used to acquire historical feedback information and corresponding historical adjustment schemes under a preset test environment based on historical tests, and form a feedback-adjustment mapping table.

[0038] The feedback mapping unit is used to input the simulated feedback information into the feedback-adjustment scheme mapping table to obtain the corresponding adjustment information of the feedback information under the preset test environment.

[0039] Preferably, the adjustment module includes:

[0040] The quantity determination unit is used to determine the adjustment amount of different valves in the corresponding simulation test chamber based on the information to be adjusted;

[0041] The verification unit is used to verify the current delivery volume corresponding to the adjustment amount of all valves and compare it with the standard delivery volume to determine whether the delivery is reasonable. The calculation process of the standard delivery volume is as follows:

[0042]

[0043] A = π(K) t (R1-Δ1)) 2

[0044] B = π(K) t (R2-Δ1)) 2

[0045] S=Y(G i (i = 1, 2, 3, ..., n1)

[0046] Among them, G i Let K1 be the target flow rate of the i-th valve, K1 be a fixed parameter, k be the gas constant, A be the first dimension of the gas pipeline before the i-th valve, B be the second dimension of the gas pipeline after the i-th valve, and K be the gas constant. t Let R1 be the radius of the gas pipeline as a function of temperature, and P1 be the radius of the pipeline before the i-th valve. i Let P2 be the total pressure of the gas pipeline before the i-th valve. i Let T1 be the total pressure of the gas pipeline after the i-th valve. i Let T2 be the gas temperature in the gas pipeline before the i-th valve. i R1 is the gas temperature in the gas delivery pipeline after the i-th valve, Δ1 is the radius error coefficient of the delivery pipeline; R2 is the radius of the delivery pipeline after the i-th valve, and ΔL is the distance between the two corresponding positions before and after the i-th valve. Indicates the pressure transmission coefficient; Y(G) represents the temperature transfer coefficient; i(i = 1, 2, 3, ..., n1) represents the delivery function based on different valves, and the number of valves is n1; S represents the standard delivery volume determined based on the delivery function;

[0047] An adjustment unit is used to control the corresponding valve to perform a first adjustment according to the information to be adjusted, if the supply is reasonable;

[0048] If the delivery is unreasonable, the component to be adjusted is locked based on the unreasonable difference and the information to be adjusted, and the component to be adjusted and the remaining valves not located on the component to be adjusted are adjusted in a second way.

[0049] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures particularly pointed out in the written description, claims, and drawings.

[0050] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0051] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0052] Figure 1 This invention provides an intake and exhaust system for a high-altitude test stand for an aero-engine.

[0053] Figure 2 This is a flowchart of the intake and exhaust system in an embodiment of the present invention. Detailed Implementation

[0054] The preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit the present invention.

[0055] This invention provides an intake and exhaust system for a high-altitude test stand for an aero-engine, such as... Figure 1 As shown, it includes:

[0056] Information acquisition module: acquires the preset test conditions and the flowchart of the intake and exhaust system, and selects a suitable test chamber as the first test chamber based on the preset test conditions;

[0057] Information analysis module: Based on the preset test conditions, perform data analysis to obtain the target operating conditions, and calculate the operating status of each valve based on the target operating conditions;

[0058] Real-time monitoring module: performs real-time monitoring of the actual operating conditions of the test chamber and obtains feedback information based on the real-time monitoring results;

[0059] Feedback adjustment module: Inputs the feedback information into the feedback-adjustment scheme mapping table, determines the different adjustment schemes corresponding to different feedback information, and adjusts the operating conditions based on the adjustment schemes.

[0060] In this embodiment, the high-altitude test stand mainly simulates the flight status and flight altitude of aero engines at different altitudes in the high-altitude test chamber, and further evaluates and assesses the engine's high-altitude performance, functional characteristics and starting characteristics.

[0061] In this embodiment, the preset test conditions refer to the basic conditions of the high-altitude environment to be simulated, including the temperature and pressure of the high-altitude environment, as well as the power requirements and engine vibration conditions corresponding to the flight state of the aircraft in the high-altitude environment.

[0062] In this embodiment, the flowchart of the intake and exhaust system is used to describe the specific operation process of the intake and exhaust system and the positional relationship of each component.

[0063] In this embodiment, data analysis refers to inputting the basic conditions of the high-altitude environment to be simulated into a trained neural network model to obtain the standard requirements that the intake and exhaust system needs to achieve. The standard requirements are the target operating conditions of the intake and exhaust system.

[0064] In this embodiment, the operation of each valve can be controlled to the target working condition. By controlling the degree of valve opening and closing, the flow rate of intake and exhaust can be controlled, thereby simulating different test conditions.

[0065] In this embodiment, the actual operating conditions refer to the specific operating conditions of the intake and exhaust systems during actual operation.

[0066] In this embodiment, feedback information refers to specific information about the actual operating conditions caused by the difference between the actual operating conditions and the target operating conditions.

[0067] In this embodiment, the feedback-regulation scheme mapping table is used to determine the valves that need to be regulated and the degree of regulation of the valves through feedback information. It is determined by comparing the actual operating conditions with the target operating conditions and determining the required regulating valves corresponding to different operating points and the degree of influence of the valve opening and closing on the gas flow rate from the intake and exhaust system flow diagram.

[0068] The beneficial effects of the above technical solution are as follows: by analyzing the preset test conditions to obtain the target operating conditions and by analyzing the flow chart of the intake and exhaust system to obtain the function of each valve in the system, by monitoring the actual operating conditions in real time and by analyzing the monitoring results to obtain the adjustment scheme to simulate the target operating conditions, and by controlling the valves to achieve the control of the target operating conditions, the specific working state of the engine under different altitude conditions can be simulated, and problems in the engine can be detected in a timely manner, which is convenient for solving the problems in the engine and can effectively ensure that the performance of the engine remains stable after it is put into service.

[0069] This invention provides an intake and exhaust system for a high-altitude test stand for an aero-engine, the intake and exhaust system comprising a test chamber 1 and a test chamber 2;

[0070] Specifically, when the preset test conditions are related to temperature, the test chamber to be simulated is determined to be test chamber 1; when the preset test conditions are related to pressure, the test chamber to be simulated is determined to be test chamber 2.

[0071] Preferably, the intake and exhaust system further includes:

[0072] Low-temperature air intake pipe, normal-temperature air intake pipe, high-temperature air intake pipe, gas transmission pipe, exhaust tower 1, exhaust tower 2, mixer, rectifier section 1, rectifier section 2, test chamber 1, test chamber 2, spray section 1, spray section 2, spray tower and oil removal equipment, air extractor and valves;

[0073] The valves include: valve D1, valve D2, valve D3, valve D4, valve D5, valve D6, valve D7, valve D8, valve D9, valve D10, valve D11, valve D12, valve D13, valve D14, valve D15, valve D16, valve D17, and valve D18.

[0074] Preferably, the connection relationships between the components include:

[0075] Valve D1 is the ambient temperature inlet valve. Valve D3 is connected to exhaust tower 1 after valve D1. Valve D2 is the cryogenic inlet valve. Valve D4 is connected to exhaust tower 1 after valve D2. Ambient temperature gas enters the gas delivery pipeline through valve D1, is diverted by valve D3, and then reaches mixer 1 through valve D5. Cryogenic gas enters the gas delivery pipeline through valve D2, is diverted by valve D4, and then reaches mixer 1 through valve D6. Mixer 1 is connected to rectifier section 1, which is located after mixer 1. Valves D7 and D8 are connected to rectifier section 1, and are located after rectifier section 1. Valves D7 and D8 are connected to test chamber 1. The gas output from rectifier section 1 reaches test chamber through valve D7 or valve D8 according to its flow rate. 1. Spray section 1 is connected to test chamber 1 after it. D9 valve is connected to spray section 1 after it. Spray tower and oil removal equipment and D10 valve are connected to D9 valve after D9 valve. D11 valve is connected to spray tower and oil removal equipment after it. Evacuation fan is connected to D11 valve after D11 valve. Exhaust tower 2 is connected to D10 valve after D10 valve. If the test conducted in test chamber 1 is a ground test, the gas output from spray tower 1 passes through D9 valve and then through D10 valve to reach exhaust tower 2. If the test conducted in test chamber 1 is a high-altitude test, the gas output from spray section 1 passes through D9 valve to spray tower and oil removal equipment and then through D11 valve to reach extraction fan.

[0076] Valve D12 is located between valves D2 and D6 and is connected to rectifier section 2. Cryogenic gas, after being diverted by valve D4, can reach rectifier section 2 via valve D12. Valve D13 is located between valves D1 and D5 and is connected to rectifier section 2. Room temperature gas, after being diverted by valve D3, reaches rectifier section 2 via valve D13. Valve D14 is the high-temperature inlet valve, connected to rectifier section 2. High-temperature gas reaches rectifier section 2 after passing through valve D14. Valve D15 is located after rectifier section 2 and connected to it. Valve D16 and D17 are located between valve D15 and valve D17. The gas is connected to valve D15, and then to test chamber 2, which is connected to valves D16 and D17. Test chamber 2 is located after valves D16 and D17. The gas output from rectifier section 2 passes through valve D15 and then, depending on the flow rate, passes through valve D16 or D17 to reach test chamber 2. Spray section 2 is located after test chamber 2 and connected to it. Valve D18 is located after spray section 2 and connected to it. Exhaust tower 2 is located after valve D18 and connected to it. The gas output from test chamber 2 first passes through spray section 2, and then passes through valve D18 to reach exhaust tower 2.

[0077] In this embodiment, the structural diagram of the intake and exhaust system is as follows: Figure 2 As shown.

[0078] The beneficial effects of the above technical solution are as follows: by collecting the preset test conditions and analyzing the flow chart of the intake and exhaust system, and effectively extracting information from the preset test conditions, the working environment of the test chamber can be effectively determined, providing favorable conditions for further selection of the test chamber. Furthermore, by analyzing the flow chart of the intake and exhaust system, the components of the intake and exhaust system and the connection relationships between the components and different valves, as well as between the components themselves, can be obtained, which helps to determine the specific location of the operating point. Moreover, based on the flow chart analysis, the function of different valves and the specific impact of different valves on the actual operating conditions can be obtained.

[0079] This invention provides an intake and exhaust system for a high-altitude test stand for an aero-engine, wherein the process analysis unit includes:

[0080] The test procedure parsing block is used to parse the test procedure and determine the test attributes of the test procedure;

[0081] When the test attributes are related to test chamber 1, close valves D12 and D13 to disconnect the compressed air from test chamber 2. Based on the flow rate at the operating point in the preset test conditions, select to open valves D7 or D8, and open valves D1 and D2 to allow low-temperature air and room-temperature dry air to pass through. Based on the flow rate and temperature at the target operating point in the preset test conditions, roughly adjust the opening of valves D3 and D4. Then adjust valves D5 and D6. Through the parameter feedback from the temperature and pressure sensors and flow meters on the pipeline, precisely adjust to the required air intake operating point of test chamber 1. The compressed air is mixed in mixer 1 to obtain compressed air with a uniform temperature. It flows through the rectifier section 1 to obtain compressed air with a uniform flow field, and then enters test chamber 1.

[0082] If the temperature of the compressed air rises after passing through test chamber 1, it will be cooled down by water spraying in spray section 1, thus reducing the exhaust temperature.

[0083] If test chamber 1 is conducting a ground test, then open valve D10 and the exhaust gas will directly enter the exhaust tower;

[0084] Otherwise, close valve D10 and open valve D11. The exhaust gas passes through the spray tower and oil removal equipment for secondary cooling, and unburned fuel in the exhaust gas is removed. Finally, the exhaust gas meets the requirements for entering the extraction unit and enters the extraction unit.

[0085] Preferably, the test procedure parsing block is further used for:

[0086] When the test attribute is related to test chamber 2, based on the temperature requirements of the air intake condition in the preset test conditions, select to open or close valves D12, D13, and D14.

[0087] If a high-temperature test is to be conducted, close valves D12 and D13, open valve D14, and select to open valve D16 or D17 based on the flow rate under the preset test conditions. The high-temperature compressed air flows through the rectifier section 2 into the test chamber 2, and the exhaust is discharged into the exhaust tower 2 after being cooled by the spray section 2.

[0088] Otherwise, close valve D14 and open valves D1 and D2 to allow low-temperature gas and room-temperature dry gas to pass through. Based on the flow rate and temperature of the target operating point in the preset test conditions, the flow rate and temperature are roughly adjusted by adjusting the opening of valves D3 and D4. Then, valves D12 and D13 are adjusted, and the required air intake operating point of test chamber 2 is precisely adjusted by the parameter feedback from the temperature and pressure sensors and flow meters on the pipeline. After flowing through the rectifier section 2, the mixed gas enters test chamber 2. The exhaust gas from test chamber 2 is cooled by the spray section and then discharged into the exhaust tower.

[0089] The beneficial effects of the above technical solution are: by analyzing the test process, it is easy to effectively determine the test chamber that needs to be simulated, ensuring the effectiveness of the simulation; by organizing the valve information, the influence of each valve on the execution process can be determined; by controlling the valves, the target working conditions under different test conditions can be achieved; the operating conditions can be controlled more conveniently and quickly to achieve the target working conditions, reducing test costs and meeting the working state requirements of the engine under different altitude conditions.

[0090] This invention provides an intake and exhaust system for a high-altitude test stand of an aero-engine, wherein the adjustment module includes:

[0091] The quantity determination unit is used to determine the adjustment amount of different valves in the corresponding simulation test chamber based on the information to be adjusted;

[0092] The verification unit is used to verify the current delivery volume corresponding to the adjustment amount of all valves and compare it with the standard delivery volume to determine whether the delivery is reasonable. The calculation process of the standard delivery volume is as follows:

[0093]

[0094] S=Y(G i (i = 1, 2, 3, ..., n)

[0095] Among them, G i Let K1 be the target flow rate of the i-th valve, K1 be a fixed parameter, k be the gas constant, A be the first dimension of the gas pipeline before the i-th valve, B be the second dimension of the gas pipeline after the i-th valve, and K be the gas constant. t Let R1 be the radius of the gas pipeline as a function of temperature, and P1 be the radius of the pipeline before the i-th valve. i Let P2 be the total pressure of the gas pipeline before the i-th valve. LLet T1 be the total pressure of the gas pipeline after the i-th valve. i Let T2 be the gas temperature in the gas pipeline before the i-th valve. i R1 is the gas temperature in the gas delivery pipeline after the i-th valve, Δ1 is the radius error coefficient of the delivery pipeline; R2 is the radius of the delivery pipeline after the i-th valve, and ΔL is the distance between the two corresponding positions before and after the i-th valve. Indicates the pressure transmission coefficient; Y(G) represents the temperature transfer coefficient; i (i = 1, 2, 3, ..., n1) represents the delivery function based on different valves, and the number of valves is n1; S represents the standard delivery volume determined based on the delivery function;

[0096] An adjustment unit is used to control the corresponding valve to perform a first adjustment according to the information to be adjusted, if the supply is reasonable;

[0097] If the delivery is unreasonable, the component to be adjusted is locked based on the unreasonable difference and the information to be adjusted, and the component to be adjusted and the remaining valves not located on the component to be adjusted are adjusted in a second way.

[0098] In this embodiment, the information to be adjusted refers to the position to which the corresponding valve should be adjusted. The flow rate corresponding to the opening degree of different positions is also different. Therefore, the corresponding adjustment amount can be determined, and the current delivery amount can be obtained. The current delivery amount can be the amount that the valve in question will pass through at the current moment. It is preset and then compared with the standard delivery amount.

[0099] In this embodiment, if the ratio of the current conveying volume to the standard conveying volume is between [0.92, 1.12], the conveying is deemed reasonable; otherwise, the conveying is deemed unreasonable.

[0100] In this embodiment, unreasonable difference refers to the difference between the current delivery volume and the standard delivery volume.

[0101] In this embodiment, the component to be adjusted may be a section of pipe consisting of several valves, and the valves in the pipe need to be adjusted.

[0102] In this embodiment, the information to be adjusted refers to the allowable adjustment of each valve, and the situation where the valve can be adjusted again based on the difference. For example, the opening degree of valve 1 is a1, the opening degree of valve 2 is a2, and the opening degree of valve 3 is a3. After adjustment based on the information to be adjusted, the opening degree of valve 1 is a01, the opening degree of valve 2 is a02, and the opening degree of valve 3 is a03. At this time, the current conveying volume is less than the standard conveying volume, so it is necessary to continue to adjust the valves according to the difference. For example, after the opening degree of valve 1 is a11, the conveying is reasonable.

[0103] The beneficial effects of the above technical solution are: by calculating the standard delivery volume, the current delivery volume under the adjustment volume is verified, ensuring the effective adjustment of the valve, avoiding simulation failure due to over-adjustment or insufficient adjustment force, and locking the adjustment component through the information to be adjusted and unreasonable differences, the valve control is corrected, ensuring the reasonable use of the test chamber in actual application.

[0104] This invention provides an intake and exhaust system for a high-altitude test stand of an aero-engine, including a real-time monitoring module, comprising:

[0105] The data calculation unit is used to obtain standard operating status data of the test chamber to be simulated under the corresponding working conditions in the preset test environment based on the test process.

[0106] The data monitoring unit is used to collect the actual operating status of the corresponding operating point during the test based on the sensor set at the corresponding operating point in the test chamber to be simulated, wherein the actual operating status is related to the detection data of the sensor type of the sensor set at the corresponding operating point;

[0107] The feedback acquisition unit is used to compare the standard operating data of the same sensor with the real-time operating status data to obtain simulated feedback information.

[0108] In this embodiment, the sensors include a temperature sensor, a pressure sensor, and a flow sensor, which are pre-set to collect operating data at different operating points.

[0109] In this embodiment, determining whether the operating conditions of each condition point meet the target operating conditions mainly depends on whether the data returned by the sensors at each condition point meets the requirements. For example, the temperature requirement for condition point 1 is 42-43℃, but the temperature returned by the sensor at condition point 1 is 40℃, then it is determined that the data of condition point 1 does not meet the target operating conditions.

[0110] In this embodiment, the comparison result includes the difference between temperature, pressure, and flow rate in the standard information and the feedback information. For example, if the standard temperature information is 45°C and the temperature in the feedback information is 50°C, then the temperature value in the comparison information is 5°C.

[0111] In this embodiment, the operating point-valve mapping table refers to the valve information that can be obtained at different operating points. The adjustment valves corresponding to the operating points between the rectifier section of test chamber 1 and test chamber 1 are valves D8 and D7.

[0112] In this embodiment, the feedback-adjustment scheme mapping table is composed of adjustment information and operating point-valve mapping table. For example, the valves corresponding to operating point 1 are valve D1 and valve D3, and the corresponding adjustment information is that valve D3 is opened 1 / 3. Then, the adjustment scheme corresponding to operating point 1 is to open valve D3 to 1 / 3.

[0113] The beneficial effects of the above technical solution are: by comparing the standard information of the target working condition with the feedback information of the actual working condition, adjustment information is obtained, the corresponding valve to be adjusted at the working condition point is determined, and the specific adjustment scheme of the valve to be adjusted is obtained through the adjustment information, which helps to achieve the purpose of obtaining the adjustment scheme through the feedback information.

[0114] This invention provides an intake and exhaust system for a high-altitude test stand of an aero-engine, including an inverse information mapping module, comprising:

[0115] The mapping acquisition unit is used to acquire historical feedback information and corresponding historical adjustment schemes under a preset test environment based on historical tests, and form a feedback-adjustment mapping table.

[0116] The feedback mapping unit is used to input the simulated feedback information into the feedback-adjustment scheme mapping table to obtain the corresponding adjustment information of the feedback information under the preset test environment.

[0117] In this embodiment, the feedback-adjustment database contains the target operating conditions of all operating points under all test environments, as well as valve information that can control the operating status of the target operating points and the valve adjustment scheme.

[0118] In this embodiment, the operating status data mainly includes temperature information, pressure information, gas flow information, and other data at the operating point.

[0119] In this embodiment, historical tests refer to all tests prior to the current time. The preset test environment is defined before the test, thereby obtaining historical feedback information under that environment, that is, the historical operation of different valves, and the adjustment scheme finally determined for different situations, thus forming a feedback-adjustment mapping table.

[0120] In this embodiment, the simulated feedback information is obtained at the current moment. Therefore, the corresponding information to be adjusted can be directly obtained according to the mapping table. For example, if the temperature is adjusted from 45 degrees Celsius to 50 degrees Celsius, the corresponding adjustment amount is to control different valves to adjust by 5 degrees Celsius.

[0121] The beneficial effects of the above technical solution are: by adjusting the feedback information of different operating conditions through the database, and by ensuring that the actual operating conditions after adjustment meet the requirements of the target operating conditions through real-time feedback information, it is possible to accurately adjust the height, Mach number and gas flow rate, so as to meet the intake and exhaust requirements of the engine or its components under different operating conditions, thereby improving the test efficiency and reducing the test cost.

[0122] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. An intake and exhaust system for a high-altitude test stand of an aero-engine, characterized in that, include: Information acquisition module: Acquires preset test conditions and structural diagrams of the intake and exhaust systems; Information analysis module: performs data analysis on the preset test conditions to obtain the target operating conditions, and determines the operating status of each valve in the exhaust pipe specified in the different test chambers in the structural diagram based on the target operating conditions; Real-time monitoring module: The simulation test chamber is tested and monitored according to the determined operating conditions, and the simulation feedback information is obtained. Information mapping module: Inputs the simulated feedback information into the feedback-adjustment scheme mapping table to determine the information to be adjusted that exists in the corresponding simulated feedback information; Adjustment module: Based on the adjustment information of different test chambers, adjusts the components of the intake and exhaust system and / or adjusts the valve operation under the corresponding test conditions; The adjustment module includes: The quantity determination unit is used to determine the adjustment amount of different valves in the corresponding simulation test chamber based on the information to be adjusted; The verification unit is used to verify the current delivery volume corresponding to the adjustment amount of all valves and compare it with the standard delivery volume to determine whether the delivery is reasonable. The calculation process of the standard delivery volume is as follows: in, Let K1 be the target flow rate of the i-th valve, K1 be a fixed parameter, k be the gas constant, A be the first dimension of the gas supply pipe before the i-th valve, and B be the second dimension of the gas supply pipe after the i-th valve. Let R1 be the coefficient of variation of the gas pipeline radius with temperature, and R2 be the radius of the gas pipeline before the i-th valve. Let be the total pressure of the gas pipeline before the i-th valve. Let be the total pressure of the gas pipeline after the i-th valve. Let be the gas temperature in the gas pipeline before the i-th valve. Let be the gas temperature in the gas pipeline after the i-th valve. This is the radius error coefficient of the conveying pipeline; 2 represents the radius of the delivery pipe after the i-th valve. This represents the distance between two corresponding points before and after the i-th valve. Indicates the pressure transmission coefficient; Indicates the temperature transfer coefficient; This represents the delivery function based on different valves, where the number of valves is n1; This represents the standard delivery volume determined based on the delivery function; An adjustment unit is used to control the corresponding valve to perform a first adjustment according to the information to be adjusted, if the supply is reasonable; If the delivery is unreasonable, the component to be adjusted is locked based on the unreasonable difference and the information to be adjusted, and the component to be adjusted and the remaining valves not located on the component to be adjusted are adjusted in a second way.

2. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 1, characterized in that, The intake and exhaust system includes test chamber 1 and test chamber 2; Specifically, when the preset test conditions are related to temperature, the test chamber to be simulated is determined to be test chamber 1; when the preset test conditions are related to pressure, the test chamber to be simulated is determined to be test chamber 2.

3. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 2, characterized in that, The intake and exhaust system also includes: Low-temperature air intake pipe, normal-temperature air intake pipe, high-temperature air intake pipe, gas transmission pipe, exhaust tower 1, exhaust tower 2, mixer, rectifier section 1, rectifier section 2, test chamber 1, test chamber 2, spray section 1, spray section 2, spray tower and oil removal equipment, air extractor and valves; The valves include: valve D1, valve D2, valve D3, valve D4, valve D5, valve D6, valve D7, valve D8, valve D9, valve D10, valve D11, valve D12, valve D13, valve D14, valve D15, valve D16, valve D17, and valve D18.

4. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 3, characterized in that, The connections between the components include: Valve D1 is the ambient temperature inlet valve. Valve D3 is connected to exhaust tower 1 after valve D1. Valve D2 is the cryogenic inlet valve. Valve D4 is connected to exhaust tower 1 after valve D2. Ambient temperature gas enters the gas delivery pipeline through valve D1, is diverted by valve D3, and then reaches mixer 1 through valve D5. Cryogenic gas enters the gas delivery pipeline through valve D2, is diverted by valve D4, and then reaches mixer 1 through valve D6. Mixer 1 is connected to rectifier section 1, which is located after mixer 1. Valves D7 and D8 are connected to rectifier section 1, and are located after rectifier section 1. Valves D7 and D8 are connected to test chamber 1. The gas output from rectifier section 1 reaches test chamber through valve D7 or valve D8 according to its flow rate.

1. Spray section 1 is connected to test chamber 1 after it. D9 valve is connected to spray section 1 after it. Spray tower and oil removal equipment and D10 valve are connected to D9 valve after D9 valve. D11 valve is connected to spray tower and oil removal equipment after it. Evacuation fan is connected to D11 valve after D11 valve. Exhaust tower 2 is connected to D10 valve after D10 valve. If the test conducted in test chamber 1 is a ground test, the gas output from spray tower 1 passes through D9 valve and then through D10 valve to reach exhaust tower 2. If the test conducted in test chamber 1 is a high-altitude test, the gas output from spray section 1 passes through D9 valve to spray tower and oil removal equipment and then through D11 valve to reach extraction fan. Valve D12 is located between valves D2 and D6 and is connected to rectifier section 2. Cryogenic gas, after being diverted by valve D4, can reach rectifier section 2 via valve D12. Valve D13 is located between valves D1 and D5 and is connected to rectifier section 2. Room temperature gas, after being diverted by valve D3, reaches rectifier section 2 via valve D13. Valve D14 is the high-temperature inlet valve, connected to rectifier section 2. High-temperature gas reaches rectifier section 2 after passing through valve D14. Valve D15 is located after rectifier section 2 and connected to it. Valve D16 and D17 are located between valve D15 and valve D17. The gas is connected to valve D15, and then to test chamber 2, which is connected to valves D16 and D17. Test chamber 2 is located after valves D16 and D17. The gas output from rectifier section 2 passes through valve D15 and then, depending on the flow rate, passes through valve D16 or D17 to reach test chamber 2. Spray section 2 is located after test chamber 2 and connected to it. Valve D18 is located after spray section 2 and connected to it. Exhaust tower 2 is located after valve D18 and connected to it. The gas output from test chamber 2 first passes through spray section 2, and then passes through valve D18 to reach exhaust tower 2.

5. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 4, characterized in that, The information analysis module includes: The process analysis unit is used to analyze the preset test conditions to obtain the test process, and to determine the specific operating status of each valve in the structure diagram based on the test process; The test procedure is the target operating condition.

6. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 5, characterized in that, The process analysis unit includes: The test procedure parsing block is used to parse the test procedure and determine the test attributes of the test procedure; When the test attributes are related to test chamber 1, close valves D12 and D13 to disconnect the compressed air from test chamber 2. Based on the flow rate at the operating point in the preset test conditions, select to open valves D7 or D8, and open valves D1 and D2 to allow low-temperature air and room-temperature dry air to pass through. Based on the flow rate and temperature at the target operating point in the preset test conditions, roughly adjust the opening of valves D3 and D4. Then adjust valves D5 and D6. Through the parameter feedback from the temperature and pressure sensors and flow meters on the pipeline, precisely adjust to the required air intake operating point of test chamber 1. The compressed air is mixed in mixer 1 to obtain compressed air with a uniform temperature. It flows through the rectifier section 1 to obtain compressed air with a uniform flow field, and then enters test chamber 1. If the temperature of the compressed air rises after passing through test chamber 1, it will be cooled down by water spraying in spray section 1, thus reducing the exhaust temperature. If test chamber 1 is conducting a ground test, then open valve D10 and the exhaust gas will directly enter the exhaust tower; Otherwise, close valve D10 and open valve D11. The exhaust gas passes through the spray tower and oil removal equipment for secondary cooling, and unburned fuel in the exhaust gas is removed. Finally, the exhaust gas meets the requirements for entering the extraction unit and enters the extraction unit.

7. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 6, characterized in that, The test procedure parsing block is also used for: When the test attribute is related to test chamber 2, based on the temperature requirements of the air intake condition in the preset test conditions, select to open or close valves D12, D13, and D14. If a high-temperature test is to be conducted, close valves D12 and D13, open valve D14, and select to open valve D16 or D17 based on the flow rate under the preset test conditions. The high-temperature compressed air flows through the rectifier section 2 into the test chamber 2, and the exhaust is discharged into the exhaust tower 2 after being cooled by the spray section 2. Otherwise, close valve D14 and open valves D1 and D2 to allow low-temperature gas and room-temperature dry gas to pass through. Based on the flow rate and temperature of the target operating point in the preset test conditions, the flow rate and temperature are roughly adjusted by adjusting the opening of valves D3 and D4. Then, valves D12 and D13 are adjusted, and the required air intake operating point of test chamber 2 is precisely adjusted by the parameter feedback from the temperature and pressure sensors and flow meters on the pipeline. After flowing through the rectifier section 2, the mixed gas enters test chamber 2. The exhaust gas from test chamber 2 is cooled by the spray section and then discharged into the exhaust tower.

8. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 1, characterized in that, The real-time monitoring module includes: The data calculation unit is used to obtain standard operating status data of the test chamber to be simulated under the corresponding working conditions in the preset test environment based on the test process. The data monitoring unit is used to collect the actual operating status of the corresponding operating point during the test based on the sensor set at the corresponding operating point in the test chamber to be simulated, wherein the actual operating status is related to the detection data of the sensor type of the sensor set at the corresponding operating point; The feedback acquisition unit is used to compare the standard operating data of the same sensor with the real-time operating status data to obtain simulated feedback information.

9. The intake and exhaust system of an aero-engine high-altitude test stand according to claim 1, characterized in that, The information mapping module includes: The mapping acquisition unit is used to acquire historical feedback information and corresponding historical adjustment schemes under a preset test environment based on historical tests, and form a feedback-adjustment mapping table. The feedback mapping unit is used to input the simulated feedback information into the feedback-adjustment scheme mapping table to obtain the corresponding adjustment information of the feedback information under the preset test environment.

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